Granted Patent B2

US 12,188,412 · App. 17/619,996 · Granted Jan 7, 2025

Inventor: Alexandre Boulzaguet (Toulouse, FR)

Assignee: SOGECLAIR SA

F02C7/14F28D7/1669F28F13/08F28D9/0012F28D19/044F28F3/08

Abstract

Claims (31)

1. A heat exchanger ( 1 ) for cooling an aircraft propulsion engine, the heat exchanger ( 1 ) having a ring-shape and comprising:

a plurality of heat exchange modules ( 2 ) which are mutually independent and being distributed circumferentially about the axis (A 1 ) of the ring,

said modules ( 2 ) being assembled with one another and being successively spaced apart in pairs,

each module comprising:

a first set of channels ( 3 a ) for the circulation of the air flow (F 1 b ) generated by the advancing aircraft;

a second set of channels ( 3 b ) for the circulation of cooling fluid,

wherein a space (E 1 ) traversed by the air flows (F 1 a ) generated by the advancing aircraft is created between two adjacent modules ( 2 ), at least one of said spaces (E 1 ) receiving at least one conductive heat-transfer element ( 7 ) extending between respective walls ( 4 ) of at least two adjacent said modules ( 2 ) which are oriented facing one another; and

wherein said at least one space (E 1 ) is closed by an external cover ( 9 a ) and an internal cover ( 9 b ) of the ring, which are respectively created on the external face ( 6 a ) and the internal face ( 6 b ) of the ring.

2. The heat exchanger ( 1 ) as claimed in claim 1 , wherein said at least one heat-transfer element ( 7 ) is integrated in at least one of said walls ( 4 ) facing one another.

3. The heat exchanger ( 1 ) as claimed in claim 1 , wherein said walls ( 4 ) facing one another inside the modules ( 2 ), of which the walls are respectively a constituent part, delimit a channel ( 3 b ) for the circulation of a cooling fluid inside the modules ( 2 ).

4. The heat exchanger ( 1 ) as claimed in claim 1 , wherein each one of the at least one conductive heat-transfer elements ( 7 ) are received in said at least one and the same space (E 1 ).

5. The heat exchanger ( 1 ) as claimed in claim 4 , wherein each one of the at least one conductive heat-transfer elements ( 7 ) are fins ( 8 ) oriented substantially, according to an overall plane extending between said walls ( 4 ) facing one another.

6. The heat exchanger ( 1 ) as claimed in claim 4 , wherein each one of the at least one conductive heat-transfer elements ( 7 ) are distributed between the modules ( 2 ) according to at least one guideline oriented parallel to a generatrix defining the surface of revolution of any one of the external face ( 6 a ) and the internal face ( 6 b ) of the ring.

7. The heat exchanger ( 1 ) as claimed in claim 1 , wherein said covers ( 9 a , 9 b ) are each formed by at least one cover element ( 10 a , 10 b ) integral with at least one of said two adjacent modules ( 2 ).

8. The heat exchanger ( 1 ) as claimed in claim 1 , wherein the constituent modules ( 2 ) of the heat exchanger ( 1 ) are produced by printing a metal in three dimensions.

9. The heat exchanger ( 1 ) as claimed in claim 1 , wherein the heat-transfer elements ( 7 ) further include fins ( 8 ), each protruding substantially, perpendicularly from one of said module ( 2 ) walls ( 4 ).

10. The heat exchanger as claimed in claim 9 , wherein each fin ( 8 ) is made in one piece with the wall ( 4 ).

11. The heat exchanger as claimed in claim 1 , wherein said module ( 2 ) walls ( 4 ) each delimit one of said second channels ( 3 b ) for the circulation of cooling fluid.

12. The heat exchanger as claimed in claim 1 , wherein at least one of said spaces (E 1 ) created between two adjacent modules ( 2 ), each heat-transfer element ( 7 ) is produced by two protruding fins ( 8 ) arranged in the extension of one another, one of the fins ( 8 ) protruding from one of said opposing walls ( 4 ) and the other of the fins ( 8 ) protruding from the other opposing wall ( 4 ).

13. The heat exchanger as claimed in claim 12 , further comprising for each heat-transfer element ( 7 ), a separating distance between the ends of the two fins ( 8 ).

14. The heat exchanger as claimed in claim 1 , wherein the first channels ( 3 a ) and the spaces (E 1 ) extend in the same direction, which is that of the air flow (F 1 a ).

15. The heat exchanger as claimed in claim 14 , wherein the second channels ( 3 b ) also extend in the same direction, which is of the air flow (F 1 a ).

16. A heat exchanger ( 1 ) for cooling an aircraft propulsion engine, the heat exchanger ( 1 ) having a ring-shape and comprising:

a plurality of heat exchange modules ( 2 ) which are mutually independent and being distributed circumferentially about the axis (A 1 ) of the ring,

said modules ( 2 ) being assembled with one another and being successively spaced apart in pairs,

each module comprising:

a first set of channels ( 3 a ) for the circulation of the air flow (F 1 b ) generated by the advancing aircraft;

a second set of channels ( 3 b ) for the circulation of cooling fluid,

wherein a space (E 1 ) traversed by the air flows (F 1 a ) generated by the advancing aircraft is created between two adjacent modules ( 2 ), at least one of said spaces (E 1 ) receiving at least one conductive heat-transfer element ( 7 ) extending between respective walls ( 4 ) of at least two adjacent said modules ( 2 ) which are oriented facing one another;

wherein each one of the at least one conductive heat-transfer elements ( 7 ) are received in said at least one and the same space (E 1 ); and

wherein since the ring has along its edge (T 1 ) a variation in thickness (Ep 1 , Ep 2 ) between its axial ends ( 5 a , 5 b ), the number of heat-transfer elements ( 7 ) varies axially (A 1 ) according to the variation in thickness (Ep 1 , Ep 2 ) of the edge (T 1 ) of the ring.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (31)